Modular nozzle ring for a turbine stage of a continuous flow machine

Abstract

The invention relates to a modular nozzle ring for a turbine stage of a continuous flow machine. The modular nozzle ring has a carrier system having an an adjustment ring, and a blade module having a blade leaf. The blade module is detachably connected to the carrier system. Furthermore, an adjustment angle of the blade leaf by the carrier system, in particular by the adjustment ring spaced apart from a flow channel, is specified, which adjustment angle is unchangeable during operation. The blade module is designed to be detachably pressed to a turbine housing part on the flow side, in particular by the adjustment ring. The invention furthermore relates to a blade module for a modular nozzle ring of a turbine stage and the use of a carrier system for a modular nozzle ring.

1 . A modular nozzle ring for a turbine stage of a turbomachine having:
 a carrier system having an adjustment ring; and   a vane module having a vane leaf,   wherein the vane module is releasably connected to the carrier system;   wherein an adjustment angle (α) of the vane leaf is fixed by the carrier system; and   wherein the vane module is configured to be releasably pressed resiliently against a flow-side turbine housing portion.   
     
     
         2 . The modular nozzle ring as claimed in  claim 1 , wherein the vane module has an axially extended vane shaft, and
 wherein the adjustment ring has a vane shaft opening,   wherein a bearing-side end portion of the vane shaft is at least partially arranged in the vane shaft opening of the adjustment ring.   
     
     
         3 . The modular nozzle ring of  claim 1 , further having a clamping element which is configured to act counter to the vane module and the carrier system. 
     
     
         4 . The modular nozzle ring as claimed in  claim 3 , wherein the clamping element is configured to axially press the vane module against the flow-side turbine housing portion. 
     
     
         5 . The modular nozzle ring as claimed in  claim 3 , wherein the clamping element is arranged between the adjustment ring and the baseplate. 
     
     
         6 . The modular nozzle ring as claimed in  claim 3 , wherein the clamping element is further configured to axially press the adjustment ring against a bearing-side housing portion of the turbomachine. 
     
     
         7 . The modular nozzle ring of  claim 1 , further having a securing element which is releasably connected to the bearing-side end of the vane shaft. 
     
     
         8 . The modular nozzle ring of  claim 1 , wherein the vane module has at a bearing-side end at least one connection element and the adjustment ring has at least one groove,
 wherein the adjustment angle (α) of the vane leaf is releasably fixed by a connection between the at least one connection element and the at least one groove.   
     
     
         9 . The modular nozzle ring of  claim 1 , wherein the vane module has a first and a second connection element, and the adjustment ring has a first and a second groove, and
 wherein the first connection element is dimensioned in accordance with the first groove and   wherein the second connection element is dimensioned in accordance with the second groove.   
     
     
         10 . The modular nozzle ring of  claim 1 , wherein the vane module has a support structure which is arranged at the bearing side of the baseplate and at a radial end portion of the vane module, wherein the at least one connection element is arranged at the bearing-side end of the support. 
     
     
         11 . The modular nozzle ring of  claim 1 , wherein the carrier system further has a carrier ring, wherein the carrier ring has an axially extended opening which is configured to receive the support structure and/or the vane shaft; and/or further having a large number of vane modules, wherein each of the vane modules is releasably connected to the carrier system. 
     
     
         12 . The modular nozzle ring of  claim 1 , wherein the vane leaf, the vane shaft, the baseplate and the support structure are integrally constructed. 
     
     
         13 . The modular nozzle ring of  claim 1 , wherein the vane module is further configured to be releasably pressed against a flow-side turbine housing portion by means of an air purge system. 
     
     
         14 . The turbine stage of a turbomachine, having a modular nozzle ring of  claim 1 . 
     
     
         15 . A vane module for a modular nozzle ring of a turbine stage, the vane module having:
 a vane leaf, and   at least one connection element which is arranged at a bearing-side end and which is configured to fix an adjustment angle (α) of the vane leaf by means of a connection between the connection element and a groove of a carrier system of the modular nozzle ring; and   wherein the vane module is configured to resiliently, releasably press against a flow-side turbine housing portion.   
     
     
         16 . The carrier system for a modular nozzle ring of  claim 1 , having an adjustment ring;
 wherein the adjustment ring has a vane shaft opening; and   wherein the adjustment ring has a first and a second groove; and   wherein the first and second grooves have different cross sections.   
     
     
         17 . The modular nozzle ring of  claim 1 , wherein the adjustment angle (α) is invariable during operation. 
     
     
         18 . The modular nozzle ring of  claim 1 , wherein the adjustment angle (α) of the vane leaf is fixed by the adjustment ring which is spaced apart from a flow channel. 
     
     
         19 . The modular nozzle ring of  claim 1 , wherein the vane module is configured to be releasably pressed resiliently by the adjustment ring against a flow-side turbine housing portion.